System and method for calibrating torque measurements

Patent metadata

Field	Value
Publication number	US-11975828-B2
Application number	US-202117363051-A
Country	US
Kind code	B2
Filing date	Jun 30, 2021
Priority date	Jun 30, 2021
Publication date	May 7, 2024
Grant date	May 7, 2024

Abstract

A torque measurement system determines torque on a shaft by monitoring angular deflection of the shaft under load using phase shift measurements. Calibration of the system uses a defined offset that is determined using a reference operating condition. The offset calibration value is determined for a rotorcraft using the following steps: defining a reference operational condition in which the shaft is rotating, estimating the torque at the reference condition based on aerodynamic knowledge of the rotors coupled to the shaft, operating the shaft at the reference operational condition, capturing sensor data to determine the phase difference at the operational condition, and associating the phase difference and an estimated torque as a calibration value to enable calculation of torque in the torque measurement system.

First claim

What is claimed is:

1. A method for calibrating a torque measurement system for a drive shaft coupled to a rotor system, comprising:
defining a reference condition in which the drive shaft is rotating;
estimating a drive shaft reference torque at the reference condition, based, at least in part, upon an aerodynamic model of the drive shaft;
operating the drive shaft at the reference condition;
capturing sensor data to determine a reference phase shift across the drive shaft at the reference condition; and
using the reference torque and the reference phase shift as a pair of calibration values for the torque measurement system.

2. The method of claim 1 , wherein the aerodynamic model defines power required versus blade pitch for the rotor system.

3. The method of claim 1 , wherein the aerodynamic model is normalized for atmospheric conditions.

4. The method of claim 1 , wherein the drive shaft is a component of an aircraft, and wherein the reference condition comprises a rotor system coupled to the drive shaft in a ready-for-flight operating configuration.

5. The method of claim 1 , wherein the drive shaft is coupled to a rotor system, and the rotor system is controlled using flight controls; and the method further comprises:
establishing the reference condition by setting a predetermined flight control position.

6. The method of claim 5 , wherein the flight controls comprise one or more of a cyclic, a collective, a pedal, and a throttle.

7. The method of claim 5 , further comprising:
providing a cockpit display to assist in setting the predetermined flight control position.

8. The method of claim 1 , wherein the drive shaft is coupled to a rotor system, and the rotor system is controlled using flight controls; and the method further comprises:
capturing sample phase shift values at a plurality of flight control positions;
identifying a lowest sample phase shift value; and
using the lowest sample phase shift value as the reference phase shift.

9. The method of claim 1 , wherein the drive shaft is coupled to a rotor system, and the rotor system is controlled using flight controls and the method further comprises:
capturing sample phase shift values at a plurality of flight control positions;
applying a curve-fit algorithm to the sample phase shift values to create a phase-shift curve;
identifying a lowest value on the phase-shift curve; and
using the lowest value as the reference phase shift.

10. A torque measurement system for a drive shaft of an aircraft, the drive shaft having a first end and a second end, the drive shaft coupled to a rotor system, wherein the rotor system is controlled using flight controls, the torque measurement system comprising:
one or more sensors configured to detect rotational positions of the first end and the second end of the drive shaft;
a calibration unit interfaced with the one or more sensors and configured to perform a calibration procedure thereon, the calibration unit comprising:
a processor; and
a memory coupled to the processor, the memory having program instructions stored thereon that, upon execution by the processor, cause the torque measurement system to:
measure a phase shift between the first end and the second end based upon the rotational positions, wherein the phase shift corresponds to a degree of twist along the drive shaft;
determine a reference phase shift at a reference operating condition established using a predetermined flight control position and corresponding to a reference torque; and
apply the reference torque and the reference phase shift as a pair of calibration values for the torque measurement system.

11. The torque measurement system of claim 10 , wherein the flight controls comprise one or more of a cyclic, a collective, a pedal, and a throttle.

12. The torque measurement system of claim 10 , wherein the program instructions further cause the torque measurement system to:
provide a cockpit display to assist in setting the predetermined flight control position.

13. The torque measurement system of claim 10 , wherein the program instructions further cause the torque measurement system to:
capture sample phase shift values at a plurality of flight control positions;
identify a lowest sample phase shift value; and
use the lowest sample phase shift value as the reference phase shift.

14. The torque measurement system of claim 10 , wherein the program instructions further cause the torque measurement system to:
capture sample phase shift values at a plurality of flight control positions;
apply a curve-fit algorithm to the sample phase shift values to create a phase-shift curve;
identify a lowest value on the phase-shift curve; and
use the lowest value as the reference phase shift.

15. A display for use in calibrating an aircraft torque measurement system, comprising:
a first section comprising drive shaft rotation speed information, the first section indicating a current drive shaft rotation speed and a target drive shaft rotation speed;
a second section comprising flight control information, the second section displaying a plurality of flight control positions, wherein each position corresponds to a different calibration operating condition, the second section further comprising a first indicator identifying a current flight control configuration and a second indicator identifying a desired flight control configuration; and
a calibration values section indicating one or more calibration values determined during a calibration procedure, the calibration procedure comprising:
defining a reference condition in which the drive shaft is rotating, the reference condition established by setting of a predetermined flight control position;
estimating a drive shaft reference torque at the reference condition;
operating the drive shaft at the reference condition;
capturing sensor data to determine a reference phase shift across the drive shaft at the reference condition; and
using the reference torque and the reference phase shift as a pair of calibration values for the calibration procedure.

16. The display of claim 15 , further comprising:
a timer section indicating a period of time during which a flight control configuration should be maintained during a calibration procedure.

17. The display of claim 15 , wherein the flight control positions comprise positions of one or more of a cyclic, a collective, a pedal, and a throttle.

18. The torque measurement system of claim 10 , wherein the program instructions further cause the torque measurement system to estimate the reference torque based, at least in part, upon an aerodynamic model of the drive shaft.

19. The display of claim 15 , wherein the calibration procedure further comprises:
capturing sample phase shift values at a plurality of flight control positions;
applying a curve-fit algorithm to the sample phase shift values to create a phase-shift curve;
identifying a lowest value on the phase-shift curve; and
using the lowest value as the reference phase shift.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Covington Charles Eric
• Tucker Brian E

Classifications

• B64C27/57 Primary

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• G01L3/109

  involving measuring phase difference of two signals or pulse trains · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• G01L25/003 Primary

  for measuring torque · CPC title